Latticed Structure for Vibration Control in Dynamic Environments

This application is a continuation of U.S. patent application Ser. No. 18/091,444, filed Dec. 30, 2022, which claims the benefit of U.S. Provisional Application No. 63/296,035, filed Jan. 3, 2022, the entire contents of each of which are incorporated by reference herein.

Various embodiments of the disclosure are directed to vibration control. Specifically, various embodiments of the disclosure are directed to lattice structure for vibration control in whole spacecraft isolation systems.

Vibration control is an increasingly important characteristic for components used in fields such as automotive, aerospace, construction, and biomedical industries. Generally stated, vibration describes a cyclical reciprocating motion that exists widely in nature and occurs for various reasons such as from movement, shock, sound, and the like. When vibration exceeds a certain limit, it can cause harm to equipment, components, structures, and even the human body. As a result, these types of excess vibrations can cause many engineering problems, such as structural failures, failure of precision equipment, and the disruption of various electronic components.

The application of vibration mitigation methods, devices, and materials has been expanded into a variety of fields, such as civil engineering, mechanical engineering, and aerospace engineering. For example, in the field of aerospace engineering, multi-dimensional vibration control has become an important consideration to ensure the safety of satellite payloads or other equipment in the launch stage. Vibrations during launch are commonly generated by flight events such as engine ignition, booster separation, and acoustic excitation, and the frequency domains of each of these excitations can be different. As a result, vibration mitigation generally requires the ability to mitigate vibrations that occur along a wide range of frequencies.

Generally, vibration mitigation in spacecraft includes both whole-spacecraft vibration isolation and micro-vibration control. Whole-spacecraft vibration isolation refers to methods and devices for the reduction of the vibration loads during launch to reduce the risk of the spacecraft and its instruments being damaged before entering orbit. The launch stage is the most severe dynamic environment that a spacecraft will experience during its mission life. To survive this stage, the structure of a spacecraft is generally strengthened by adding mass/structure that will be useless once the spacecraft is in orbit. This not only increases launch costs, but also reduces the mass margin that could be used for launching additional payload. Micro-vibration control refers to the methods and devices for the reduction of risk of damage to instruments or components from vibration after launch while the spacecraft or satellite is in orbit. Both passive vibration control devices and active vibration control devices have been used however, active vibration control devices have generally demonstrated vibration control performance at greater cost and complexity.

Over the past few decades, effort has been made by researchers toward vibration mitigation methods, devices, and materials in spacecraft and other applications. For example:

Jun et al.,-Proc. Inst. Mech. Engineers Part G J. Aerospace Eng. 221, 67-72 (2007) discloses an active vibration control device for whole-spacecraft vibration isolation which includes a plurality of isolator devices inserted between a launch vehicle and a payload adaptor. In addition, passive constrained layer damping (PCDL) material is attached to the outer surfaces of the payload adapter.

Tang et al.,--J. Aerospace Eng. (2018) discloses an active whole-spacecraft isolation system based on voice coil motors (VCMs). The Tang system includes VCMs, supporting leaf springs, and actuator supports that are placed between a launch vehicle and the payload adaptor. As such, the tang system can satisfy the design requirement of vibration isolation with the addition of the VCMs and associated components without changing the payload adaptor fitting structure itself.

Rittweger et al.,5, In Spacecraft Structures, Materials and Mechanical Testing 2005, 581 (2005) discloses an active payload adaptor for reduction of interface loads to the payload in the low frequency domain (<100 Hz). The Rittweger adaptor consists of two interface rings connected by 24 active struts. The dynamic load transfer to the launcher goes via a structural path through the payload adaptor, which makes the structural connection from launcher payload to the launcher.

Liu et al.,-J. Sound Vibration 289, 726-744 (2006), presents an octo strut passive vibration isolation platform for replacement of an existing payload attaching fitting to provide an interface between a launch vehicle and a spacecraft.

Liu, F., Fang, B., and Huang, W. H. (2010). “Vibration control of flexible satellites using a new isolator,” In 2010 3rd International Symposium on Systems and Control in Aeronautics and Astronautics Harbin: IEEE, 593-597, (2010), presents a Circular Payload Adapter Fitting (CPAF) which integrates passive and active vibration control with piezoelectric stack actuators.

Chi et al.,--Sensors and Smart Structures Technologies for Civil, Mechanical, and Aerospace Systems, Vol. 9061. 90613X1-90613X-7, (2014), presents a voice-coil motor designed and optimized as an active control actuator to provide proper feedback force to reduce the amplitude of the vibration and is fixed in the whole-spacecraft vibration isolation platform, with sensors collocated on one side of the voice-coil motor in the vertical direction.

As seen in Rittweger, and Liu 2006, researchers have explored the use of strut-based structures to enhance the mechanical vibration isolation properties of a machine frame and reduce mass while also conserving structural integrity. However, in the case of the Rittweger device are, the vibration control device is designed as an active device that depends on hydraulic struts configured to adjust to control vibration. The use of active vibration control devices adds cost and complexity to the design along with increased chance for component failure from the vibration control components. In the case of Liu, the device applies the design concepts of a Stewart platform for whole-spacecraft passive vibration isolation. The Liu device adds redundancy to a traditional Stewart platform design by adding redundant struts to the platform for the purpose of safety and reliability.

Outside of the specific realm of spacecraft, researchers have additionally explored the use of additive manufacturing or 3D printing to create strut-based structures to enhance the mechanical vibration isolation properties of a machine frame. For example, Syam et al.,-Precision Engineering (2017) presents an additive manufacturing lattice design used for a vibration isolation structure.

There is still a need to continually investigate and improve the properties of the vibration mitigation materials. As such, improvements to vibration mitigation and control devices would be well received.

One or more embodiments of the disclosure are directed to a tuned lattice attenuator and methods for tuning a lattice attenuator for customized dynamic mechanical loading.

In various fields such as automotive, aerospace, construction, and biomedical industries, dynamic environments such as shock, vibration, acoustics, and the like, can be a significant design constraint. For example, in aerospace applications among others, dynamic environments can present the most detrimental loading case for onboard electronics, avionics, ordnance, pneumatic components, and the like, and can impact the functionality or cause component damage. As a result, dynamic environments can in some instances result in total system failure via damage to one or more critical components.

Generally, there have been multiple approaches to address the problems posed by dynamic environments. These approaches have included designing hardware to be more tolerant of the dynamic environment or isolating the hardware from the dynamic environment using a mechanical interface. In many instances however, designing hardware to be tolerant of dynamic environments is not possible due to technical constraints, schedule or cost constraints, or the severity of the dynamic environment.

As such, isolation systems are more often used for vibration control. However, isolation systems possess their own disadvantages. For example, to protect a specific component multiple isolators may be required. Depending on the weight of the supported hardware the isolators themselves must be appropriately selected and sized based on the supported hardware's natural frequency. Furthermore, mounting hardware is also required to secure each isolator. This includes fasteners, washers, and standoffs where necessary. This increases part quantity, complexity and adds to system mass. As another example, once a component is isolated it is no longer secured to the substrate, meaning that it is more susceptible to adverse temperature change. To protect the component, a heat sink bracket or other thermal management system may be required. These add design and manufacturing costs.

Further, once a component is isolated it may lose its electrical ground path. This means that a metal grounding strap may be required for every component and especially for avionics electronics or other electronics. Still further, often times acceptance testing of isolators by themselves is required to demonstrate/verify lot performance. Isolators are then tagged as sets to be installed together which requires tracking and verification. Lastly, larger systems such as aircraft, amphibious vehicles, underwater vehicles, and launch vehicles may have dozens if not hundreds of components requiring isolation. This adds meaningful costs in labor, documentation, and tracking requirements that can add up at a system level, despite being small individually. Aside from cost, this creates a meaningful amount of system wide “parasitic mass”—mass which exists solely to reduce dynamic environments. Parasitic mass results in efficiency losses in less mass-sensitive applications but can become a matter of critical concern in more mass-sensitive applications such as spacecraft design. Finally, all of these activities can contribute to more prolonged manufacturing schedules.

In light of these issues, various embodiments of the disclosure provide a dynamic environment isolator/vibration control device that can address the problems inherent with existing isolation systems. In one or more embodiments the attenuator comprises a latticed support structure that can be used to mitigate dynamic environments in a system by isolating connected elements from a vibration source. Further, in various embodiments, due to the nature of latticed structures, embodiments can function as a drop-in replacement to an existing structure or component in a system that provides vibration attenuation/control while also preserving the same or a similar structural strength as the replaced structure/component. As such, various embodiments allow for “plug and play” use in existing/legacy systems without requiring a redesign or significant modification. For example, in various embodiments existing legacy components can simply be removed and replaced by embodiments of the disclosure that maintain similar shape, size, and structural characteristics to support loads but in contrast with the replaced component include inherent vibration attenuating/isolating characteristics as a result of a latticed structure/design.

Because the latticed support structure provides inherent vibration control, various embodiments altogether can eliminate the need for isolation at individual or localized levels. Depending on the application, components may be connected to or hard mounted to a lattice support structure thereby eliminating need for isolators, standoffs, associated mounting hardware, brackets, grounding straps, or the like. For example, the avionics cylinder of the Minotaur IV S4 rocket required over 200 individual isolators—amounting to a large amount of system-wide parasitic mass.

In one or more embodiments the parasitic mass of these traditional vibration isolating devices is eliminated. As a result, various embodiments can provide improved performance capabilities and significantly reduce costs. For example, embodiments can improve payload capacity of launch vehicles by reducing parasitic mass. For instance, certain embodiments could result in increases to payload capacity by 13%. In addition, various embodiments can result in significant reductions to design costs via the simplification or elimination of vibration control analysis. Similarly, manufacturing schedules can be shortened and/or standardized due to the “plug and play” nature of various embodiments. For example, soft ride systems used to mitigate vehicle transient loads into spacecraft can cost upwards of $300K to $600K in development costs with 12-18 month added development time. In various embodiments these costs and the added development time can be substantially reduced or even eliminated. For example, various embodiments can result in launch vehicle cost reductions of approximately 16%.

As such, one or more embodiments are directed to a vibration control system for whole-spacecraft vibration isolation. In various embodiments the system comprises a payload interface cone for connection between a spacecraft vibration source and a load. In various embodiments the payload cone includes a first support structure, a second support structure, and a sidewall extending between the first and second support structures and defining a frustoconical body of the payload interface cone. The sidewall is configured to structurally support the load against the second support structure such that the load is isolated from the spacecraft vibration source. In one or more embodiments the sidewall includes one or more lattice portions occupying at least part of a total area of the sidewall. In various embodiments the lattice portions are configured to attenuate a transfer of vibrations through the sidewall between the first and second support structures for reducing vibration transfer from the spacecraft vibration source and the load. In various embodiments the frustoconical body of the payload interface cone is approximately the same as a component without one or more lattice portions such that the payload interface cone is a drop-in replacement component. In certain embodiments, the system does not include independent dampening devices such as springs or the like for vibration attenuation.

The above summary is not intended to describe each illustrated embodiment or every implementation of the present disclosure.

While the embodiments of the disclosure are amenable to various modifications and alternative forms, specifics thereof have been shown by way of example in the drawings and will be described in detail. It should be understood, however, that the intention is not to limit the disclosure to the particular embodiments described. On the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the disclosure.

Referring to, a vibration control deviceA,B is depicted, according to one or more embodiments of the disclosure. In various embodiments the vibration control deviceA,B is a structural component of a vibration isolation system that functions to physically support and/or isolates a loadfrom a vibration sourceto protect the loadfrom potential vibration damage. In such embodiments, the vibration control deviceA,B is a sub-component or sub-system of a larger system where the supported loadis isolated or protected from dynamic environments. For example, in various embodiments the deviceA,B is part of a whole-spacecraft isolation system configured to isolate an attached payload that is included in a launching space vehicle. However, this is only an example use and in various embodiments the deviceA,B could be a component of any suitable type of vibration isolation system such as those used in automotive, medical devices, or other types of systems. In one or more embodiments the supported loadis connected to the vibration sourceonly through the deviceA,B. However, in certain embodiments the supported loadcould be supported by a plurality of vibration control devices or other structural components. In some embodiments the vibration device could be directly connected or indirectly connected to the loadsuch that one or more other components may be positioned between the device and the load itself.

In various embodiments, the vibration control deviceA,B includes one or more structural features that inhibit or attenuate the transmission of vibrations from the vibration sourceto the supported load. As such, when connected to the deviceA,B the loadwill generally possess a vibration amplitudethat is reduced relative to a vibration amplitudeat the vibration source. For example, referring additionally to, a high-level view of a vibration control deviceand a graph illustrating the effect of vibration control are depicted, according to one or more embodiments of the disclosure. Referring specifically to, a simple example is depicted where vibration is transferred from an external vibration sourceto a load, which in various embodiments can be a machine, structure or other system component that requires some amount of protection from dynamic environments.

In such embodiments loadis protected from a vibration sourcevia the vibration control devicethat both supports the loadand reduces the effect of source vibrationon the supported load. For example, in various embodiments the deviceis constructed from structure that having structural characteristics and/or material that function to isolate, dampen, or otherwise attenuates the transfer of source vibrationto the load. For example, depicted in, the devicefunctions both as an isolatorand as a dampener. For example, in various embodiments the isolatorcan be used to reduce the vibration amplitudethat is transferred to the machine, with respect to the external vibration, by separating the loadfrom the external vibration source. In one or more embodiments, the ratio of the reduced vibrationseen by the loadvs the source vibration, indicates the extent of the isolation from external vibration. In various embodiments dampenerhas a damping coefficient that can be the result of a damping component/material or can be from the structure of the deviceitself.

The result of vibration control is depicted in the graphof, which considers a two scenarios where vibration is transferred from the vibration sourceto the loadthrough different embodiments of a vibration control device. For instance, graphconsiders a first embodimentwhere a vibration control deviceis configured as an isolator but does not include damping characteristics and a second embodimentwhere the vibration control deviceis both configured as an isolator and includes damping.

In, the y-axis indicates a ratioof the vibration amplitude experienced by the loadversus the vibration amplitude experienced by the vibration sourcewhile the x-axis indicates a ratiobetween a frequency f of vibration experienced by the loadverses a natural frequency fof the load. As such, in one or more embodiments, the loadis considered to become one structure with the external vibration sourcewhen the fraction of the transferred displacement to the load is equal to 1 as in such instances the loadis experiencing the same vibration amplitude as the source. Further, in various embodiments when the ratio between f and the natural frequency fis equal to 1, the vibration amplitude of the loadwill be amplified due to the effects of natural resonance. As such, depicted in, the first embodiment and second embodiment of the devicefunction as vibration isolators by reducing the vibration amplitude ratiobelow 1 as the vibration ratiomoves further from the resonance frequency for the load. Further,depicts that in the second embodiment, the vibration damping characteristics of the devicefunctions to reduce the maximum vibration amplitude rationear the resonance frequency as compared to the undamped embodiment.

Described further below, in various embodiments the deviceadditionally functions to move or shift the natural frequency fof the attached load. In such embodiments, by shifting the natural frequency fthe maximum vibration amplitudeexperienced by the loadcan be shifted to a desired frequency—for example a frequency where the loadis most capable of tolerating vibration forces. For example, the attached loadmay have a higher tolerance for vibrations located at a particular wavelength such that by shifting the natural frequency to that wavelength the load can be protected via the greatest vibration amplitude occurring where the load is most suited to withstand vibration.

Depicted inthe deviceA,B is configured as a latticed vibration control device. It has been observed by the inventors that lattice structures allow for a high-efficiency vibration isolation structure that additionally present sufficient structural integrity to sustain a load. As such, in various embodiments utilize a latticed sidewall design to replace portions of existing components or to create new components that possess the same size/shape as previous components and the same or similar structural integrity but with vibration control characteristics integrated into the component itself. As such, various embodiments can function as a drop-in replacement to an existing structure or component in a system that provides vibration attenuation/control while also preserving the same or a similar structural strength as the replaced structure/component.

In one or more embodiments the deviceA,B includes a frame structure including a first support structureand a second support structurethat are attached respectively to the vibration sourceand the supported load. In various embodiments the first and second support structures,are generally solid portions of the device that are configured to attach to the loadand/or vibration source. As such, in various embodiments the support structures can also be referred to as a top portion or bottom portion of the device, or support platform, or the like. In various embodiments the deviceA,B includes a latticed sidewallA,B that makes up the body of the device and connects the first and second support structures,. In such embodiments the sidewallA,B is configured to support a structural load applied to the first and second support structures,—such as supporting the load on a vibration source.

In various embodiments the latticed sidewallA,B includes one or more latticed portionsthat occupy at least a portion of a total area of the sidewallA,B. In various embodiments the latticed portionsare configured to attenuate the transferof vibrations between the first support structureand the second support structureby inhibiting the transmission of vibrationsthrough the connecting sidewallA,B. As such, in one or more embodiments the lattice design will improve and/or alter the isolation/damping characteristics of the device. For example, in certain embodiments the isolator can shift the natural frequency of the attached load and control device to attenuate vibrations in a specific way such that attached loads can be kept within acceptable vibration thresholds.

Specifically, depicted in, the device includes a sidewallA with a generally cylindrical shape, for example, where the device is configured as cylindrical support, while depicted in, the sidewallB has a frustoconical shape, for example where the device is configured as a payload cone or as a bulkhead.

Depicted in, the sidewallA,B includes a plurality of latticed portionsthat are defined as sections of latticed sidewall between one or more latitudinally extending hoops. In various embodiments, the hoopsextend about the circumference of the sidewall and provide additional structural integrity for the device. Further, described further below, in various embodiments the hoopsallow for the use of different lattice designs or placements of latticed portions within the sidewall by segregating or separating different portions of the sidewall from one another. Depicted in, the plurality of latticed portions includes seven latticed portionsthat occupy 90% or greater of the total area of the sidewallA,B. However, in various embodiments, the sidewallA,B could include a fewer number or greater number of latticed portions and could occupy a larger or smaller percentage of the total area of the sidewallA,B. For example, in various embodiments the sidewallA,B could include a single lattice portion that occupies nearly 100% of the total area of the sidewall. In certain embodiments the plurality of latticed portions includes two or more lattice portions where the two or more lattice portions each occupy 10% to 50% of the total area of the sidewall. In certain embodiments, the sidewallA,B could include several smaller individual lattice portions that together make up only approximately 33% of the total area of the sidewallA,B. In various embodiments the vibration control device could have two or more latticed portions that are adjacent in the sidewall or non-adjacent. For example, in certain embodiments a latticed portion could be separated from another lattice portion by a solid portion/non-latticed portion of the sidewall. In various embodiments the total area occupied by the latticed portions is 5% to 100% of the total area of the sidewall. Described further below, in various embodiments the lattice portions can be constructed using a variety of different lattice designs to adjust/control the natural frequency based on the vibration control/structural integrity requirements of the device. In such embodiments, the plurality of lattice patterns could share the same pattern or have different patterns.

For example, referring to, various embodiments of cylindrical vibration control devices are depicted, according to one or more embodiments of the disclosure. The devicesA-F include a top support structure, a bottom support structure, and a cylindrical latticed sidewallA-F connecting the top and bottom support structures,and defining a cylindrical structure that is configured to support/displace a structural load between a vibration source and a supporting load. As such, in various embodiments the top and bottom support structures,can be positioned between a load and a vibration source with the latticed sidewall providing structural support to maintain the separation while also providing vibration attenuation to reduce transmission of vibration through the device as described above. However,depict vibration control devicesA-F having various different configurations of lattice designs for a vibration control device sidewall. In various embodiments, the lattice design will alter the isolation/damping characteristics of the device. For example, in certain embodiments the specific lattice designs can shift the natural frequency of the attached load and control device to attenuate vibrations in a specific way such that attached loads can be kept within acceptable vibration thresholds throughout use.depict various configurations for lattice sidewalls, with each sidewall presenting a different vibration control profile relative to one another. In various embodiments, the appropriate lattice sidewall configuration can be selected or used based on the vibration control requirements of the load.

For example, referring to the table below the various embodiments ofpresent different natural frequencies relative to one another. Described further below, the configuration ofcan referred to as a baseline configuration withbeing variations of the baseline configuration of. In that vein the table below includes a rock ratio and bounce ratio showing the differences between each embodiment in their natural resonance frequency as compared to thebaseline.

In such a manner, existing payload support systems for spacecraft launch vehicles can be easily and quickly modified to include the appropriate vibration damping characteristics by replacing one or more standard components with an embodiment of the present disclosure that have been configured with latticed sidewalls for vibration damping functionality. For example, in various embodiments the devices ofcould be substituted for existing structural components in a rocket to adapt the rocket for vibration damping to protect a supported load. In such a manner various embodiments can allow for the reduction of or even the elimination of separate vibration control devices in a spacecraft, thereby reducing mass and improving payload efficiency.

Referring specifically to, the lattice sidewallA includes a plurality of latticed portionsthat are defined by a plurality of longitudinally extending hoopswhich segregate/distinguish each of the lattice portionsas described above. In, the lattice design of each of the lattice portionsare aligned with one another such that the sidewall forms a continuous helical pattern that extends between the top and bottom support portions,. Depicted in, while the lattice portionsare configured with a lattice pattern that possesses a helical design, however, in various embodiments the exact type and design of the pattern can differ. In one or more embodiments the configuration ofcould be referred to as a baseline configuration withbeing variations of the baseline configuration of.

For example,depicts a variation of the baseline design ofwhere the lattice sidewallB, includes two lattice portionsthat are rotated about a central axis relative to the other lattice portions. As such, the plurality of latticed portions includes a first and second lattice portionhaving a first lattice pattern and a second lattice portionhaving a second lattice pattern. Specifically, inthe top two lattice portionsare rotated such that the helical lattice of the top two portionsare radially offset from lattice portionand the top portionsand bottom portionsmeet at a midspan between the vertically extending

, depicts a variation of the baseline design ofwhere the lattice sidewallC includes lattice portionsthat are each rotated about a central axis relative to adjacent lattice portionssuch that each lattice portionincludes helical lattice that hits midspans of adjacent lattice portions.depicts a variation of the baseline design ofwhere the lattice sidewallD includes lattice portionseach rotated every row by a small angle relative to adjacent lattice portions. Specifically, the lattice portionsare rotated such that the helical design of the portionsare rotated by a small angle but not an angle sufficient such that the lattice portions hit midspans of adjacent lattice portions.

depicts a variation of the baseline design ofwhere the lattice sidewallE includes only three lattice portions,,. In various embodiments hoopscan be added or removed as needed to adjust the number of defined lattice portions. As such, with the removal of two central hoops the sidewallE now only includes three lattice portions for example including a first and second lattice portion,each occupying approximately 20% of the total area of the sidewallE and a third lattice portionoccupying approximately 60% of the total area of the sidewall.depicts a variation of the baseline design ofwhere the lattice sidewallF includes two lattice portionswith lattice that has a different thickness in the lattice structure than a remainder of the lattice portions. Specifically, lattice portionshave a thicker lattice structure as compared to the lattice structure of lattice portions. As such, in various embodiments, the lattice design of the sidewall can include portions with variable thickness or different types of materials. For example, in certain embodiments some or all of the lattice portions could be constructed from different types of materials and/or have different thicknesses.

Referring toa spacecraft systemof the prior art is depicted. In, the systemincludes a loadand a payload interface system. In various embodiments the payload interface systemincludes various components including a payload cone or interface conewith one or more connected damping elementsthat are configured to attach to and support the loadfor launch. As described above, the payload interface systemis a whole-spacecraft vibration isolation system configured for reduction of vibration imparted to the load. As such, the payload systemis designed to reduce the risk of damage to the spacecraftor its instruments before entering orbit. To survive this stage, payload interface systemprovides supporting structure such as the payload coneand damping elementsto dampen and/or isolate the loadfrom source vibration. As such, the payload interface provides a structural element for supporting the loadwhile the damping elementsinclude various isolator components such as springs, damping material, or the like, to inhibit the transfer of vibration from the spacecraft to the load. As such, the damping elementscan be used to reduce the vibration amplitudetransferred to the load, with respect to the source vibration.

Depending on the weight of the load, the isolators themselves must be appropriately selected and sized based on the supported load'snatural frequency. Furthermore, mounting hardware is also required to secure each isolator. This includes fasteners, washers, and standoffs where necessary Further, a heat sink bracket or other thermal management system may be required along with various grounding straps.

Referring to, various embodiments of a whole spacecraft isolation systemincluding a vibration control deviceare depicted, according to one or more embodiments of the disclosure. Specifically,depicts a cross-sectional plan view of the vibration control device as part of a whole spacecraft isolation systemwith an attached loadwhiledepicts a partial perspective view of the vibration control device.

In various embodiments vibration control deviceis the same or substantially similar to vibration control deviceB described above with reference to. For example, in one or more embodiments the vibration control deviceincludes a frame structure including a first support structureand a second support structurethat are attached respectively to the vibration sourceand the supported load. In various embodiments the first and second support structures,are generally solid portions of the device that are configured to attach to the loadand a vibration source. As such, in various embodiments the support structures can also be referred to as a top portion or bottom portion of the device.

In various embodiments the deviceincludes a latticed sidewallconnecting the first and second support structures,. In such embodiments the sidewallis configured to support a structural load against the first and second support structures,. In various embodiments latticed portionsof the sidewallare configured to attenuate a transfer of vibrations between the first support structureand the second support structureby inhibiting the transmission of vibrationsthrough the sidewall. For example, in one or more embodiments the lattice design will alter the isolation/damping characteristics of the devicesuch that the device naturally possesses vibration attenuation characteristics without the use of independent dampening devices such as springs or the like such as shown in. In certain embodiments the devicecan shift the natural frequency of the attached loadand control device to attenuate vibrations in a specific way such that attached loads can be kept within acceptable vibration thresholds.